Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1986-02-18
1987-03-03
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F41G 700
Patent
active
046469907
ABSTRACT:
A coil (21) mounted inside a spinning guided object (20) has an electrical current (i) induced therewithin by means of interaction with the earth's magnetic field (B). A similar coil (22) mounted on the launch platform spins at the same rate (W) as the object's coil (21), although these two coils (22, 21) are not necessarily in phase. Apparatus (35) associated with the launch platform generates a constant phase signal (P) having amplitude and sign representing the phase difference between the signal generated by the launch platform's coil (22) and the vertical direction. This phase information (P) is used to correct the guidance commands sent from the launch platform to the guided object (20), or, alternatively, is fed directly to the guided object (20) for correction by said object's on-board computer. A hold fire indicator (33) is provided to inform the operator when the output from the launch platform's coil (22) is above or below a predetermined level sufficient for adequate roll angle compensation.
REFERENCES:
patent: 3397358 (1968-08-01), Allenden et al.
patent: 3414215 (1968-12-01), Martin et al.
patent: 3860199 (1975-01-01), Dunne
patent: 4109199 (1978-08-01), Ball et al.
patent: 4114451 (1978-09-01), Crittenden et al.
patent: 4166406 (1979-09-01), Maughmer
patent: 4328938 (1982-05-01), Reisman et al.
Ford Aerospace & Communications Corporation
Jordan Charles T.
Radlo Edward J.
Zerschling Keith L.
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